Rocket-like aerial toy



Dec. 18, 1962 1.. w. BROWN ETAL 3,068,792

ROCKET-LIKE AERIAL TOY Filed March 6. 1959 4 Sheets-Sheet 1 INVENTORSLawrence WBmwn, Her-her! D-Brown an BY Paul E. Brown.

Dec. 18, 1962 w. BRXOWN ETAL 3,068,792

ROCKET-LIKE AERIAL TOY 4 Sheets-Sheet 2 Filed March 6. 1959 mm W Tmw Mma w mwafi N m 5 wru ae 2 m Y 7 B Dec. 18, 1962 w. BROWN ETAL 3,0

ROCKET-LIKE AERIAL TOY 4 Sheets-Sheet 3 Filed March 6, 1959 IN VEN TORSLawrence W- Brown,

rt .D. Brown and y Paul E. Brown.

H erbe ATTORNEYS.

4 Sheets-Sheet 4 Dec. 18, 1962 1.. w. BROWN ETAL ROCKET-LIKE AERIAL TOYFiled March 6. 1959 j INVENTORS Lawrence W- Brown,

4% ATTORNE ye.

Herbert D. Brown and BY Paul E Brown.

3,068,792 RQCKET-LIKE AERIAL TOY Lawrence W. Brown, Herbert E). Brown,and Paul E. Brown, Clinton, Men; Herbert D. Brown, administrator ofLawrence W. Brown deceased, assignor of one-third to said Herbert D.Brown, said iaul E. Brown, Matilda Walker and Helen Long, all ofClinton, Me.

Filed Mar. 6, 1959, Ser. No. 797,7d 3 Claims. (Cl. 102-341) Thisinvention relates to rockets and like aerial missile toys, and moreparticularly to such devices which are propelled by discharge of gasesformed by burning of a propellant charge positioned therein.

The principal objects of the present invention are to provide a missilein the form of a projectile of separable parts which are propelled intothe air in assembled condition by the burning of a propellant thereinand at the end of the burning of said propellant the separable parts areexpelled one from the other; to provide a missile in the form of aprojectile which is propelled into the air by a propellant and whichafter a substantially predetermined period of travel will discharge aconnected descent retarding device for slowing the fall of the missile;to provide such a missile having a tubular body with a descent retardingdevice removably enclosed in one end and a rocket shell or engineremovably mounted in the other end; to provide such a missile whereinthe rocket shell or engine is a casing enclosing a propellant chargewith a jet aperture in the rear end whereby the burning of thepropellant charge forms gases for discharge through the aperture toeffect propulsion of the missile; to provide such a missile includingconnected tubular body, nose member and descent retarder wherein therocket shell has an explosive charge in the forward end thereof which isignited at the end of the burning of the propellant charge and expelsthe nose member and descent retarder from the body near the end of itsupward travel; to provide a missile in the form of a projectile having atubular body with a rocket shell or engine removably mounted in one endwith said rocket engine including a casing enclosing a propellant chargewith a jet aperture in the rear end for discharge of gas from burning ofsaid charge for propulsion of the missile; to provide such a missilewith a guide track or tube on the body and a launcher wherein said guidetrack slidably engages an elongate launching guide rod of the launcherto guide the missile in its initial motion; and to provide such amissile toy that is inexpensive, highly entertaining and that may berecovered and reused repeatedly.

Other objects and advantages of this invention will become apparent fromthe following description taken in connection with the accompanyingdrawings wherein are set forth by way of illustration and examplecertain embodiments of this invention.

FIG. 1 is a side elevation of a missile embodying the features of thepresent invention mounted on a launching guide with portions broken awayto illustrate the structure.

FIG. 2 is a longitudinal sectional view through the missile in assembledcondition.

P16. 3 is an elevational view of the upper portion of the missile bodywith the nose member and descent retarder connected thereto andpositioned for retarding descent thereof.

FIG. 4 is an enlarged sectional view through the forward portion of themissile to illustrate the arrangement of the descent retarder in thenose member in assembled position.

FIG. 5 is a transverse sectional view through the missile body on theline 55, FIG. 2.

FIG. 6 is a disassembled perspective view of the parts of the missile.

nited States 1.; atent lCC FIG. 7 is a side elevational view of themissile with a modified form of descent retarder.

FIG. 8 is a longitudinal sectional view through a further modified formof missile.

FIG. 9 is a partial longitudinal sectional view through the missileshown in FIG. 8 with the parts separated after burning of thepropellant.

Referring more in detail to the drawings:

1. generally designates an aerial missile consisting of a body 2 with anose member 3 at the forward end 4 of the body and a descent retarderdevice 5 enclosed in the nose member 3 and a rocket shell or engine 6removably positioned in the rearward end 7 of said body.

The body 2 preferably is an elongate tube made of lightweight materialsuch as suitable synthetic resin or aluminum or formed of tightly rolledpaper whereby said body is substantially non-inflammable. The missilebody preferably has a through longitudinal axial bore 8 whereby the wall9 of the body is substantially of uniform thickness. A plurality ofguide fins 10 are suitably secured to the rearward portion adjacent therear end 7 of the body 2 and extend substantially radially therefrom incircumferentially spaced relation. In the illustrated structure, theguide fins 10 are mounted on a sleeve 11 having a through longitudinalbore 12 of a size that said sleeve is pressed onto the rear portion ofthe body in tight engagement therewith. The fins 10 and sleeve 11 arepreferably made of synthetic resin or other suitable material and thefit of the sleeve on the body normally will retain the sleeve in placethereon, however, the anchor for the sleeve may be enhanced by asuitable adhesive or the like if desired. The fins have forward andrearward edges 14 and 15 respectively inclined rearwardly and outwardlyfrom the body, as illustrated in FIG. 2. The fins are also preferablyinclined relative to a longitudinal axial plane whereby during flightair movement by the fins tends to eifect rotation of the missile aboutthe axis thereof. A guide tube or track 16 is secured to the missilebody and is adapted to engage a launcher. guide 17 to guide the missileduring its initial movement. In the illustrated structure, a small tube18 is suitably secured to the side of the body 2 and extendinglongitudinally thereof. The tube 18 has a longitudinal bore 19 extendingtherethrough with the axis thereof parallel to the axis of the body 2.The tube 18 is suitably secured to the body 2 by suitable fasteningmeans such as adhesive or giue 2d and is positioned whereby the rearwardend 21 is spaced slightly forwardly of the forward end of the sleeve ll,and the forward end 22 of said tube 18 is spaced substantiallyrearwardly of the forward end 4 of the body member. However, the guidetube is of suitable length to provide sufficiently long engagement withthe launcher guide 17 to maintain the missile in alignment therewith. Anannular collar 23 is inserted in the forward end of the body 2 andpreferably positioned adjacent the forward end 22 of the guide tube 18to provide a shoulder 24 spaced rearwardly from the forward end 4 of thebody for sufiicient insertion of the nose member in the body as laterdescribed. The annular collar 23 is preferably a press fit into the bore8 of the body 2 whereby friction will hold it in place; however, it maybe further secured by suitable adhesive, if desired. The collar 23 has abore 25 extending axially therethrough, as illustrated in FIG. 4.

The nose member 3 is preferably molded of synthetic resin or othersuitable material and has an ogive forward end or nose 26 with therearward portion thereof merging in a cylindrical portion 27 preferablysubstantially the same diameter as the outer diameter of the body 2. Therearward portion 28 of the nose member is reduced in size whereby theouter surface thereof conforms to the inner surface of the forwardportion of the body rnember 2. The rearward portion 28 of the nosemember is inserted into the body member and the frictional engagement ofthe nose member portion 28 in the bore 8 of the body 2 forms areleasable connection whereby the nose member may be expelled from thebody 2 as later described. The nose member 3 has an axial cavity 29opening from the rear end- 30 thereof and terminating in spaced relationto the forward end as at 31. The rear end opening of the cavity 29 isclosed by a plug 32 having a head portion 33 engaging the rear end 30 ofthe nose member which is preferably spaced from the forward end of thecollar 23 a distance corresponding to the thickness of the plug head 33.When the shoulder 34 on the nose member engages the forward end of thebody member 2, the plug 32 has a shank portion 35 extending into therear portion of the cavity 29 and has a loose fit therein. The forwardend of the plug shank has a socket 36 extending therein to receive awedge member or cork 37 cooperating with the plug in securing a line 38thereto. The forward end of the nose member has an aperture 39 and aresilient cord or band 40 has one end 41 extending through the apertureand anchored in the cavity 29. The resilient cord or band 40 extendsoutwardly of the nose member and along the side thereof andlongitudinally of the body member 2 and has the other end connected toan anchor 42 spaced from the forward end of the body 2. The anchor 42preferably consists of a plurality of strips of adhesive tape 43 woundaround the body member 2 and guide tube 18 as illustrated in FIG. 2. Theresilient band 40 is preferably of such length that it is under tensionwhen the nose member 3'is inserted in the forward end of the bodywhereby the tension of the resilient cord aids in holding the nosemember in said body member. The end of the cord 40 in the cavity 29 ispreferably connected to one end of the line 38 which line extends intothe socket 36 under the cork 37 and out the opposite side whereby saidline is secured to the plug 32 by' the cork, with the length of the linebetween the plug and the end secured to the resilient band beingsubstantially greater than the length of the nose member. The otherportion 44 of the line 38 extends from the plug and is attached as at 45to a descent retarding device 5.

In the structure illustrated in FIGS. 1 to 6 inclusive, the descentretarder consists of a flexible strip 46 such as thin synthetic resinwith the end portions folded over a stiffener such as rods 47. The stripis rolled and the line wound therearound and inserted in the cavity 29and then the plug 32 inserted in the rear end of the nosemember and thenose member inserted in the body in the positions illustrated in FIG. 4.

The rocket shell or engine 6 preferably consists of a tube 48 madesubstantially non-inflammable by forming same of tightly rolled paper.The rear end of the tube 48 is closed by an end member or plug 49preferably formed of ceramic material. The end member 49 has a tight fitinto the bore 50 of the tube 48, and, if desired, may be cemented orotherwise secured in place with the rear face 51 of the end member flushwith the rear end of the tube 48. The forward end of the end member 49is preferably provided with a conical socket 52 adapted to receive aconical projection 53. on a propulsion charge 54, said charge preferablyconsisting of suitable propellant powder, for example, black powderpressedinto a cylindrical shape to fit into the bore 50 of the tube 48It is preferable that the propulsion charge 54 have a slow burningportion 54 adjacent the end member 49 and a faster burning portion 54"extending from the portion 54 toward the other end of the tube 48. Thisprovides a short period of burning before the initial movement of themissile. The end member 49 is provided with an axial aperture 55 of suchsize to receive a standard size fuse 56 of suitable length whereby theinner end of said fuse rests in the recess or socket 52 in contact withthe charge 54 so any burning of the fuse will ignite said charge. I Thefuse 56 is preferably held' in the aperture by an adhesive 'when theforward end of the tube 48 engages a stop ring 57' secured in the body 2as illustrated in FIG. 2. The quantity of the propulsion charge 54 issuch that in burning it will provide substantially the duration of theflight desired, and at the forward end of said charge is a second charge58 providing a slower burning and a time delay before ignition of anexplosive charge 59 at the forward end of the charge 58. Suitablepacking or wadding 60 is pressed into the forward end of the tube 48 incontact with the explosive charge 59.

The launcher 17. preferably consists of a block 61 having a plurality oflegs 62 extending outwardly and downwardly whereby when the ends of thelegs 62 are engaged with the ground or supporting surface 63 the block61 is positioned whereby a guide member 64 extends from the upper end 65of the block in an upright position. The guide member 64 is preferably aslender tube with a rod 66 sleeved in the upper end thereof whereby saidrod may be detached for carrying purposes, but when positioned forlaunching the rod 66 extends the length of the launcher guide.

The operation of the aerial. toy constructed as described is as follows:

The body 2, with the nose member 3 and descent retarder 5- assembled andpositioned as illustrated in FIG.

4, is then provided with the rocket shell or engine 6 V which is.inserted into the rear end of the body bore 8 preferably until theforward end engages the stop ring 57. The rocket shell 6 forms asubstantially gas-tight fit in said body bore 81 whereby the engagementof the tube 48 with the wall 9 of the body forms a removable mountingfor the rocket shell 6. The missile is then moved to the upper end ofthe launcher guide rod 66 in its extended position, and the rod 66inserted through the bore 19 of the guide track 18, and the missilelowered on the launcher guide until the lower end' of the rocket shellrests on the upper end 65 of the block 61, as illustrated in FIG. 1. Thefuse 56 is then ignited, and the burning of the fuse will direct theflame into the recess 52 to the conical projection of the propellantcharge 54 to' ignitesame creating gases which will escape through thejet aperture 55. The burning of the portion 54' of the charge provides ashort period of gas discharge for sound'and visual effects. Then theportion 54 of the charge is ignited and the force of the escaping gasesfrom the faster burning charge through the aperture 55 will provide ajet action which will cause the. missile to be propelled upwardly alongthe launcher guide member to direct themissile path. As the missileleaves the launcher guide rod 66, air pressure on the vanes 10 willcause an axial rotation of the 'missile to aid in maintaining it in a'straight lineof flight. When the propellant charge is burned, thedelayed action charge 58 is. ignited'and burns and will ignite theexplosive charge 59 at approximately the peak of the flight of -themissile. create a force propelling the. packing60 forwardly, and alsothe gases from the explosive charge will cause a pressure on the plug 32expelling same together with the nose member 3 fromthe body 2 of themissile. The resilient cord or band 40 will pull the forward end of thenose member 3 adjacent to the forward end of themissile body. 2 and. theplug 32 beingloose in the nose member will fall therefrom drawingout'the descent retarder '5 whereby during the free falling of themissile the nose member, plug and, descent retarder will be positionedas During the descent, the flexible ment'which is effective in retardingthe descent of the The explosive charge will missile. After the missileis retrieved, the descent retarding device 5 is again rolled andpositioned in the nose member 3, and the nose member 3 and plug 32reassembled on the missile body. The spent rocket engine 6 is thenremoved from the rear end of the missile body and a new rocket engine 6inserted in its place and the missile is ready for reuse. The bore 57"in the stop ring 57' may be made smaller than the bore 50 of the tube 48whereby the pressure of the gases from the explosive charge 59 will acton the rocket shell and the plug 32 whereby the spent rocket engine orshell and nose member will be expelled substantially simultaneously fromthe body 2.

In the form of the invention illustrated in FIG. 7, the structure of themissile and parts thereof are substantially the same as illustrated inFIGS. 1 to 6 inclusive, with the exception that the descent retarder isin the form of a parachute 67 having shrouds 60 connected as at 69 tothe end of the portion 44 of the line 38. The use and operation of themissile illustrated in FIG. 7 is substantially the same as describedrelative to the form of the invention illustrated in FIGS. 1 to 6inclusive.

In the form of the invention illustrated in FIGS. 8 and 9, the body 79is an elongate tube that is substantially the same as the body 2 of theform of the invention illustrated in FIGS. 1 to 6 inclusive, with theexception that the collar 23 is omitted and a solid plug 71 is arrangedin the body bore 72 in place of the stop ring 57', these changes beingfor manufacturing economy as the body 2 could be used without change andthe plug 71 inserted to close the bore through the stop ring 57'. Thebody 70 has guide fins and a tube 18 secured thereto in the same mannerand performing the same function as the corresponding parts in the formof the invention illustrated in FIGS. 1 to 6 inclusive. A nose member 73preferably formed of molded flexible synthetic resin, such aspolyethylene or polyvinylchloride or other suitable material, with anogive forward end or nose 74 merging in a cylindrical portion 75preferably substantially the same diameter as the outer diameter of thebody 70. The forward end portion preferably has a thin wall 76 to form aresilient end or cushion when the missile falls and the nose strikes theground or other solid body. The rearward portion 77 of the nose memberis reduced in size whereby it is inserted in the forward end of the body70 and forms a tight fit therein to retain the nose member assembled onthe body. The rocket engine or shell 78 is substantially the same as therocket engine or shell 6 as shown in FIG. 2, with the exception that theslow charge 58 and explosive charge 59 and wadding 60 are omitted.

In the operation of the aerial toy constructed as illustrated in FIGS. 8and 9, the body 70 and nose member 73 are assembled and positioned asillustrated in FIG. 8, and then a rocket shell or engine 78 is insertedinto the rear end of the body 70 with the forward end of the shell orengine engaged with the plug 71. The missile is then moved to the upperend of the launcher guide rod 66 in its extended position, and the rod66 inserted through the bore of the guide track or tube 18 and themissile lowered on the launcher guide until the lower end of the rocketshell rests on the upper end of the block 61. The fuse of the rocketshell is then ignited and the burning of the fuse will direct the flameinto the propellant charge portion 54 whereby the slower burning portionof the charge will provide a short period of gas discharge for sound andvisual efiects. Then the fast burning portion of the propellant charge54" is ignited, and the force of the gases from the faster burningportion of the charge escaping through the jet aperture 55 will providea jet action causing the missile to be propelled upwardly along thelauncher guide member to direct the missile path. At the end of theburning of the propellant charge portion 54" the gases therefrom actingon the plug 71 and end member 49 of the rocket engine or shell willexpel the spent rocket engine from the body 70. This lightens the weightat the rear of the missile whereby when it reaches the peak of theflight it will then fall nose first to the ground, and the thin wall ofthe nose member will cushion the impact of the device when it hits theground. The missile body and nose member can then be retrieved and a newrocket engine 78 inserted and the missile is ready for reuse.

It is to be understood that while we have illustrated and describedcertain forms of our invention, it is not to be limited to the specificforms or arrangements of parts herein described and shown except insofaras such limitations are included in the claims.

What we claim and desire to secure by Letters Patent 1. A rocket-likemissile device comprising, a cylindrical body having a longitudinalaxial bore, a nose member having one end removably sleeved into one endof the body bore, stabilizing means mounted on the body adjacent theother end thereof, said nose member having a recess therein opening fromsaid one end of the nose member in the body, a descent retarder in saidnose member recess, a plug loosely closing said nose recess, an elongateflexible member connecting said descent retarder to said nose plug andsaid nose plug to said nose member in separable relation, meansconnecting said nose member to said body in separable relation, anelongate propellant container removably sleeved in said body bore atsaid other end of the body for substantially the length of saidcontainer, means in said body engaging said container and limitingmovement thereof toward said nose member, a jet aperture in the rear ofsaid propellant container and axially thereof, means extending throughsaid jet aperture for igniting propellant in the container thereforadjacent said jet aperture whereby progressive burning of the propellantforms gases for discharge through the jet aperture axially of said bodyto propel the missile, and an explosive charge at the end of thepropellant for ignition at the end of the burning of said propellant andforcing the nose member from the body whereby the plug in the nosemember moves therefrom pulling the descent retarder out of the nosemember for operation in slowing the descent of the missile.

2. A rocket-like missile device comprising, a cylindrical body having alongitudinal axial bore, a nose member having an ogive nose at one endand the other end removably sleeved into one end of the body bore,stabilizing means mounted on the body adjacent the other end thereof,said nose member having a recess therein opening from said other end ofthe nose member, a descent retarder in said nose member recess, a plugloosely closing said nose recess, an elongate flexible member connectingsaid descent retarder to said nose plug and said nose plug to said nosemember in separable relation, means connecting said nose member at theforward end thereof to said body in separable relation, an elongatepropellant container having a propellant charge therein removablysleeved in said body bore at said other endof the body for substantiallythe length of said conta ner, a jet aperture in the rear of saidpropellant container and axially thereof, means extending through saidjet aperture for igniting the propellant charge adjacent the rear ofsaid propellant container whereby progressive burning of the propellantcharge forms gases for discharge through the jet aperture axially ofsaid body to propel the missile, an exp osive charge at the end of thepropellant charge for ignition at the end of the burning of saidpropellant to force the nose member from the body whereby the plug inthe nose member moves therefrom pulling the descent retarder from saidnose member for operation in slowing the descent of the missile, and aguide means extending longitudinally of said body for following a fixedpath during launching movement.

3. A rocket-like missile device comprising, a cylindrical body having alongitudinal axial bore, a nose member having an ogive nose at one endand a cylindrical portion at the other end sleeved into one end of thebody bore,

member, a descent retarder in said nose member recess,

an elongate flexible member connecting said descent retarder to saidnose plug and said nose plug'to said nose member in separable spacedrelation with the nose plug betweensaid nose member and descentretarder, a resilient cord connecting the forward endof said nose memberto said body in separable relation, a tubular guide track secured tosaid body and extending longitudinally thereof, alauncher guide havingan upright slender shaft, said tubular guide having a longitudinal borewhereby said guide is'loosely sleeved over said launcher shaft, anelongate tubular propellant container removably sleeved in said bodybore at said other end of the body for sub stantially the length of saidpropellant container, a noninflammable plug in the rear end of saidcontainer and having an axial aperture extending therethrough, a closuremember sleeved into the forward end of said container,

a; propellant charge in said container between the plug and closuremember, a fuse extending through said plug aperture and engaging thepropellant charge adjacent said non-inflammable plug whereby ignition ofthe fuse effects ignition of the propellant charge and progressiveburning of same forms gases for discharge through said aperture in anaxial jet propelling said body, an explosive charge at the end of thepropellant charge remote from said plug for igniting at the end of theburning of said propellantcharge and forcing the closure member fromsaid shell through the body bore to impact the nose plug and force saidnose'member and connected plug from the body whereby the nose plug movesfrom the nose member and pulls the descent retarder therefrom and theflexible member permits separation and release of the descent retarderto slow descent of the missile.

References Cited in the file of this patent UNITED STATES PATENTS DeckerNov. 21, 1937 Campbell Sept. 6, 1955 C arlisle July 1, 1958

